No abstract

The topical problem of choosing the standard size of the unified space platform developed by the joint-stock company «Academician M. F. Reshetnev» Information Satellite Systems» for geostationary communication satellites has been formulated. Previously, the task of assessing the effectiveness of using the developed unified platforms for creating a new spacecraft was solved to a greater extent empirically, by generalizing the groundwork for existing developments and assessing the possibility and feasibility of using the existing groundwork in the future (development continuity). However, a methodological basis for solving this kind of problem has not yet been developed. As part of the study, a model for assessing the efficiency of a spacecraft based on a unified space platform was developed. A method for evaluating the effectiveness of the use of unified space platforms with an excess resource (in terms of mass and energy consumption) for the payload and a method for evaluating the effectiveness of using a modernized unified space platform, which makes it possible to meet increased resource requirements (in terms of weight and energy consumption) for the payload, have been developed. With the help of the developed methods, the assessment of the range of effective use of a unified space platform for geostationary communication satellites developed by JSC ISS was carried out, both without revision and with the necessary modernization for a specific project (payload).

This paper considers the basic technologies of active removal of space debris from the geostationary orbit. For two of them: coupling of service spacecraft (SC) with the space debris item with the help of an arm of the service SC (rigid link) and capture of the space debris object with a net or a harpoon (flexible link),-a list of main disturbing moments is given, influencing the service SC during the coupling and space debris towing to the graveyard orbit. A comparative analysis of resource intensity has been performed of various schemes for space debris removal with rigid or flexible link.

An economic efficiency model of spacecraft is developed. Besides, such economic efficiency indicators as profitability index and payback period of a project are designed. This model is modified to calculate the economic efficiency of a service spacecraft and as a result an overall index of project efficiency is developed on its basis. This index results in minimized interruptions when the system point is used in the geostationary orbit. The analysis of conditions for the effective use of service spacecraft aimed at the removal of space debris from the geostationary orbit is carried out; the recommendations on its operating performance are made.

The paper considers the service spacecraft (SSC) with electric propulsion system (EPS) to approach the objects of space debris (OSD) and its transportation into a disposal orbit. It suggests the SSC operation algorithm and different ways to ensure its implementation. The paper also provides the equations of SSC motion at optimal control, gives design-ballistic analysis alongside with the calculation of the required resources for the SSC operation.